Attitude data and configuration. More...

Inheritance diagram for EECFI.Attitude:

Public Member Functions
	Attitude () throws CfiError
	Empty Class constructor.
	Attitude (final TimeCorrelation timeId, final SatNomTransId satNomTrId, final SatTransId satTrId, final InstrTransId instTrId) throws CfiError
	Constructor with satellite frame ids.
void	close () throws CfiError
	Release all resources managed by this object.
void	setTransformations (final TimeCorrelation timeId, final SatNomTransId satNomTrId, final SatTransId satTrId, final InstrTransId instTrId) throws CfiError
	Set the transformations in the attitutde Id.
native void	compute (final ModelId modelId, final StateVector stateVector, long targetFrame) throws CfiError
	Compute attitude matrix.
native void	userSet (final ModelId modelId, final StateVector stateVector, long targetFrame, final double[][] matrix, final double[][] matrixRate, final double[][] matrixRateRate, final double[] offset) throws CfiError
	Assign user-defined attitude frame.
native AttRec	getAttitudeData (long dataType, long sourceRefType, long sourceRef) throws CfiError
	Compute quaternions/angles equivalent to the transformation from sourceRef to the attitude target frame.
native AttitudeData	getData () throws CfiError
	Get attitude id data.
native void	setData (final AttitudeData attitudeData) throws CfiError
	Set attitude id data.
native Coord	changeFrame (final SatId satId, final ModelId modelId, long modeFlag, long frameFlagIn, long frameIdIn, long frameFlagOut, long frameIdOut, final StateVector satStateVec, final Coord statVecIn) throws CfiError
	Change the input vector/direction from a coordinate system to another ( including attitude frames ).

Detailed Description

Attitude data and configuration.

Constructor & Destructor Documentation

EECFI.Attitude.Attitude ( ) throws CfiError

Empty Class constructor.

EECFI.Attitude::Attitude	(	final TimeCorrelation	timeId,
		final SatNomTransId	satNomTrId,
		final SatTransId	satTrId,
		final InstrTransId	instTrId
	)			throws CfiError

Constructor with satellite frame ids.

Parameters:

	timeId	Time correlations.
	satNomTrId	Satellite nominal attitude.
	satTrId	Satellite attitude.
	instTrId	Instrument attitude.

Member Function Documentation

Coord EECFI.Attitude::changeFrame	(	final SatId	satId,
		final ModelId	modelId,
		long	modeFlag,
		long	frameFlagIn,
		long	frameIdIn,
		long	frameFlagOut,
		long	frameIdOut,
		final StateVector	satStateVec,
		final Coord	statVecIn
	)			throws CfiError

Change the input vector/direction from a coordinate system to another ( including attitude frames ).

This method changes the coordinate or attitude frame of a location or direction by keeping the location or direction in inertial space identical.

Both all coordinate frames and all attitude frames are supported. When changing the frame for a location, the difference in origin of the frames is taken into account. While when changing the frame for a direction, the target is assumed to be at infinity.

Parameters:

	satId	Satellite id.
	modelId	Model id.
	modeFlag	Selection of location or direction calculus (ModeFlagPointingEnum).
	frameFlagIn	Selection of coordinate or Attitude frame on input (FrameFlagEnum).
	frameIdIn	Coordinate frame id or attitude frame id on input (AttFrEnum or CsRlEnum).
	frameFlagOut	Selection of coordinate or Attitude frame on output (FrameFlagEnum).
	frameIdOut	Coordinate frame id or attitude frame id on output (AttFrEnum or CsRlEnum).
	satStateVec	State vector with time, time reference, position, velocity and acceleration of satellite (Earth fixed CS).
	statVecIn	Coordinates to be transformed in input frame (deriv indicates if pos, pos and vel or pos, vel and acc is to be calculated).

Returns:: Tranformed coordinates in ouput frame.

void EECFI.Attitude.close ( ) throws CfiError

Release all resources managed by this object.

IMPORTANT: The life time of the EOCFI Java objects must be explicitly managed by the program work flow. Failure to perform this release will lead to resource leakage and might have a significant impact in performance.

void EECFI.Attitude::compute	(	final ModelId	modelId,
		final StateVector	stateVector,
		long	targetFrame
	)			throws CfiError

Compute attitude matrix.

This method calculates the Attitude Frame for a given S/C state vector.

Note: it can be internally applied a correction to computations in order to compensate for the travel time of light from the Sun to the Earth and the satellites orbiting it. To activate this compensation, the Sun model in xl_model_id must be initialized with the enum XL_MODEL_SUN_TRAVEL_TIME using the function xl_model_init (see [LIBSUM]).

Parameters:

	modelId	Model Id.
	stateVector	State vector which contains time reference, time, position, velocity and acceleration needed for computation. Coordinates must be in Earth Fixed reference frame.
	targetFrame	Attitude frame (AttFrEnum).

AttRec EECFI.Attitude::getAttitudeData	(	long	dataType,
		long	sourceRefType,
		long	sourceRef
	)			throws CfiError

Compute quaternions/angles equivalent to the transformation from sourceRef to the attitude target frame.

This method computes the quaternions or Euler angles that returns the transformation between the sourceRef frame and the target frame defined in the attitude object.

Parameters:

	dataType,:	requested data type: quaternions or angles
	sourceRefType	Source reference frame type: external or satellite
	sourceRef,:	Source reference frame

Returns:: Attitude record with the time and quaternions or angles.

AttitudeData EECFI.Attitude::getData ( ) throws CfiError

Get attitude id data.

Returns:: Attitude data.

void EECFI.Attitude::setData ( final AttitudeData attitudeData ) throws CfiError

Set attitude id data.

Parameters:

attitudeData

Attitude data.

void EECFI.Attitude::setTransformations	(	final TimeCorrelation	timeId,
		final SatNomTransId	satNomTrId,
		final SatTransId	satTrId,
		final InstrTransId	instTrId
	)			throws CfiError

Set the transformations in the attitutde Id.

Parameters:

	timeId	Time correlations.
	satNomTrId	Satellite nominal attitude.
	satTrId	Satellite attitude.
	instTrId	Instrument attitude.

void EECFI.Attitude::userSet	(	final ModelId	modelId,
		final StateVector	stateVector,
		long	targetFrame,
		final double	matrix[][],
		final double	matrixRate[][],
		final double	matrixRateRate[][],
		final double[]	offset
	)			throws CfiError

Assign user-defined attitude frame.

Parameters:

	modelId	Model Id.
	stateVector	State vector with time, time reference, position, velocity and acceleration needed for computation.
	targetFrame	Attitude frame ID (AttFrEnum).
	matrix	Matrix represeting the transformation from ToD to targetFrame.
	matrixRate	Matrix represeting the transformation rate from ToD to targetFrame.
	matrixRateRate	Matrix represeting the transformation rate rate from ToD to targetFrame.
	offset	Offset in the reference frame origin.

Generated on Mon Dec 11 2023 14:48:29 for by

1.7.1

EECFI.Attitude Class Reference

Public Member Functions

Detailed Description

Constructor & Destructor Documentation

Member Function Documentation